Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il)
Reynolds number: 1,000,000
Max Cl/Cd: 111.89 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ls421-il-1000000.txt
Download as CSV file: xf-ls421-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY LS(1)-0421 AIRFOIL                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.0906   0.08018   0.07589  -0.0722   1.0000   0.0238
 -19.500  -1.0931   0.07641   0.07204  -0.0739   1.0000   0.0239
 -19.250  -1.0939   0.07291   0.06846  -0.0754   1.0000   0.0241
 -19.000  -1.0935   0.06958   0.06505  -0.0768   1.0000   0.0242
 -18.750  -1.0920   0.06640   0.06180  -0.0782   1.0000   0.0244
 -18.500  -1.0894   0.06341   0.05874  -0.0794   1.0000   0.0245
 -18.250  -1.0925   0.05989   0.05515  -0.0807   1.0000   0.0247
 -18.000  -1.0949   0.05649   0.05170  -0.0818   1.0000   0.0250
 -17.750  -1.0935   0.05357   0.04873  -0.0828   1.0000   0.0252
 -17.500  -1.0880   0.05096   0.04607  -0.0842   0.9793   0.0255
 -17.250  -1.0832   0.04873   0.04375  -0.0845   0.9545   0.0258
 -17.000  -1.0779   0.04686   0.04179  -0.0842   0.9374   0.0261
 -16.750  -1.0717   0.04499   0.03982  -0.0841   0.9248   0.0264
 -16.500  -1.0632   0.04331   0.03805  -0.0840   0.9143   0.0267
 -16.250  -1.0546   0.04161   0.03627  -0.0840   0.9054   0.0270
 -16.000  -1.0438   0.04011   0.03469  -0.0840   0.8972   0.0274
 -15.750  -1.0331   0.03864   0.03312  -0.0839   0.8891   0.0277
 -15.500  -1.0203   0.03730   0.03171  -0.0840   0.8834   0.0280
 -15.250  -1.0123   0.03562   0.02997  -0.0838   0.8770   0.0283
 -15.000  -1.0057   0.03389   0.02816  -0.0835   0.8706   0.0288
 -14.750  -0.9945   0.03253   0.02676  -0.0834   0.8654   0.0293
 -14.500  -0.9816   0.03131   0.02551  -0.0832   0.8606   0.0297
 -14.250  -0.9673   0.03028   0.02443  -0.0830   0.8556   0.0302
 -14.000  -0.9529   0.02926   0.02335  -0.0827   0.8505   0.0307
 -13.750  -0.9376   0.02832   0.02234  -0.0825   0.8454   0.0313
 -13.500  -0.9206   0.02746   0.02145  -0.0824   0.8418   0.0317
 -13.250  -0.9068   0.02640   0.02034  -0.0821   0.8375   0.0322
 -13.000  -0.8946   0.02525   0.01915  -0.0816   0.8332   0.0330
 -12.750  -0.8786   0.02438   0.01825  -0.0812   0.8288   0.0336
 -12.500  -0.8614   0.02361   0.01742  -0.0810   0.8243   0.0343
 -12.250  -0.8430   0.02287   0.01667  -0.0808   0.8217   0.0350
 -12.000  -0.8238   0.02220   0.01596  -0.0807   0.8186   0.0357
 -11.750  -0.8056   0.02146   0.01519  -0.0804   0.8153   0.0363
 -11.500  -0.7903   0.02055   0.01426  -0.0799   0.8118   0.0373
 -11.250  -0.7718   0.01986   0.01355  -0.0796   0.8083   0.0382
 -11.000  -0.7521   0.01927   0.01291  -0.0794   0.8039   0.0391
 -10.750  -0.7313   0.01872   0.01234  -0.0793   0.8014   0.0401
 -10.500  -0.7119   0.01807   0.01167  -0.0790   0.7988   0.0411
 -10.250  -0.6937   0.01736   0.01096  -0.0786   0.7960   0.0424
 -10.000  -0.6739   0.01680   0.01040  -0.0782   0.7932   0.0436
  -9.750  -0.6561   0.01633   0.00989  -0.0774   0.7902   0.0447
  -9.500  -0.6363   0.01582   0.00935  -0.0770   0.7873   0.0460
  -9.250  -0.6140   0.01530   0.00882  -0.0772   0.7838   0.0477
  -9.000  -0.5892   0.01487   0.00838  -0.0776   0.7812   0.0496
  -8.750  -0.5638   0.01439   0.00791  -0.0782   0.7794   0.0518
  -8.500  -0.5373   0.01394   0.00748  -0.0789   0.7772   0.0548
  -8.250  -0.5103   0.01351   0.00707  -0.0797   0.7748   0.0589
  -8.000  -0.4829   0.01310   0.00670  -0.0804   0.7724   0.0646
  -7.750  -0.4553   0.01271   0.00635  -0.0811   0.7702   0.0731
  -7.500  -0.4273   0.01232   0.00601  -0.0818   0.7679   0.0840
  -7.250  -0.3988   0.01195   0.00571  -0.0826   0.7655   0.0969
  -7.000  -0.3698   0.01163   0.00544  -0.0835   0.7627   0.1113
  -6.750  -0.3403   0.01129   0.00518  -0.0845   0.7603   0.1284
  -6.500  -0.3102   0.01092   0.00492  -0.0856   0.7589   0.1473
  -6.250  -0.2797   0.01055   0.00467  -0.0867   0.7571   0.1698
  -6.000  -0.2487   0.01015   0.00441  -0.0880   0.7551   0.1977
  -5.750  -0.2171   0.00973   0.00415  -0.0895   0.7531   0.2330
  -5.500  -0.1848   0.00932   0.00391  -0.0910   0.7512   0.2734
  -5.250  -0.1522   0.00895   0.00370  -0.0926   0.7493   0.3118
  -5.000  -0.1190   0.00861   0.00350  -0.0943   0.7474   0.3510
  -4.750  -0.0854   0.00827   0.00331  -0.0960   0.7453   0.3926
  -4.500  -0.0514   0.00796   0.00315  -0.0978   0.7428   0.4374
  -4.250  -0.0166   0.00764   0.00302  -0.0998   0.7400   0.4916
  -4.000   0.0177   0.00739   0.00295  -0.1015   0.7388   0.5408
  -3.750   0.0508   0.00730   0.00295  -0.1027   0.7374   0.5699
  -3.500   0.0832   0.00728   0.00296  -0.1037   0.7356   0.5860
  -3.250   0.1155   0.00729   0.00296  -0.1047   0.7336   0.5986
  -3.000   0.1475   0.00729   0.00300  -0.1055   0.7316   0.6084
  -2.750   0.1796   0.00733   0.00301  -0.1064   0.7295   0.6166
  -2.500   0.2113   0.00734   0.00303  -0.1072   0.7274   0.6235
  -2.250   0.2429   0.00739   0.00308  -0.1080   0.7251   0.6294
  -2.000   0.2747   0.00748   0.00312  -0.1088   0.7224   0.6346
  -1.750   0.3065   0.00757   0.00318  -0.1096   0.7193   0.6394
  -1.500   0.3376   0.00756   0.00322  -0.1103   0.7170   0.6452
  -1.250   0.3690   0.00757   0.00324  -0.1110   0.7139   0.6488
  -1.000   0.4004   0.00757   0.00323  -0.1117   0.7103   0.6518
  -0.750   0.4318   0.00757   0.00321  -0.1124   0.7061   0.6545
  -0.500   0.4631   0.00763   0.00321  -0.1131   0.7013   0.6567
  -0.250   0.4946   0.00767   0.00323  -0.1139   0.6980   0.6585
   0.000   0.5259   0.00761   0.00320  -0.1147   0.6948   0.6615
   0.250   0.5568   0.00759   0.00320  -0.1153   0.6902   0.6642
   0.500   0.5874   0.00761   0.00320  -0.1158   0.6840   0.6670
   0.750   0.6179   0.00768   0.00326  -0.1163   0.6784   0.6705
   1.000   0.6488   0.00771   0.00332  -0.1170   0.6738   0.6737
   1.250   0.6797   0.00774   0.00334  -0.1176   0.6683   0.6759
   1.500   0.7102   0.00781   0.00336  -0.1182   0.6623   0.6778
   1.750   0.7412   0.00785   0.00341  -0.1189   0.6569   0.6793
   2.000   0.7719   0.00784   0.00340  -0.1195   0.6497   0.6815
   2.250   0.8016   0.00788   0.00341  -0.1200   0.6414   0.6838
   2.500   0.8320   0.00789   0.00345  -0.1206   0.6327   0.6857
   2.750   0.8611   0.00798   0.00351  -0.1209   0.6217   0.6875
   3.000   0.8905   0.00807   0.00358  -0.1213   0.6077   0.6891
   3.250   0.9186   0.00821   0.00366  -0.1214   0.5892   0.6907
   3.500   0.9449   0.00845   0.00380  -0.1212   0.5644   0.6923
   3.750   0.9685   0.00884   0.00402  -0.1206   0.5281   0.6939
   4.000   0.9894   0.00936   0.00433  -0.1195   0.4862   0.6957
   4.250   1.0090   0.00993   0.00469  -0.1182   0.4454   0.6974
   4.500   1.0278   0.01049   0.00506  -0.1167   0.4092   0.6988
   4.750   1.0462   0.01103   0.00543  -0.1152   0.3755   0.7000
   5.000   1.0630   0.01158   0.00582  -0.1134   0.3456   0.7010
   5.250   1.0788   0.01206   0.00619  -0.1115   0.3189   0.7032
   5.500   1.0896   0.01255   0.00658  -0.1085   0.2970   0.7055
   5.750   1.0996   0.01313   0.00707  -0.1055   0.2768   0.7075
   6.000   1.1136   0.01378   0.00764  -0.1034   0.2571   0.7095
   6.250   1.1283   0.01445   0.00823  -0.1015   0.2393   0.7114
   6.500   1.1435   0.01513   0.00884  -0.0998   0.2228   0.7133
   6.750   1.1589   0.01584   0.00947  -0.0982   0.2075   0.7151
   7.000   1.1746   0.01655   0.01012  -0.0968   0.1941   0.7168
   7.250   1.1905   0.01728   0.01080  -0.0954   0.1822   0.7185
   7.500   1.2060   0.01806   0.01152  -0.0940   0.1715   0.7201
   7.750   1.2230   0.01876   0.01218  -0.0928   0.1630   0.7215
   8.000   1.2395   0.01951   0.01290  -0.0917   0.1554   0.7226
   8.250   1.2566   0.02023   0.01359  -0.0906   0.1486   0.7250
   8.500   1.2734   0.02097   0.01434  -0.0896   0.1424   0.7275
   8.750   1.2902   0.02172   0.01508  -0.0885   0.1368   0.7297
   9.000   1.3060   0.02254   0.01590  -0.0874   0.1315   0.7319
   9.250   1.3230   0.02330   0.01666  -0.0864   0.1273   0.7341
   9.500   1.3383   0.02417   0.01751  -0.0853   0.1226   0.7362
   9.750   1.3549   0.02498   0.01833  -0.0844   0.1191   0.7383
  10.000   1.3710   0.02582   0.01918  -0.0834   0.1156   0.7402
  10.250   1.3853   0.02678   0.02011  -0.0822   0.1116   0.7420
  10.500   1.4014   0.02764   0.02099  -0.0813   0.1088   0.7436
  10.750   1.4169   0.02854   0.02190  -0.0803   0.1060   0.7452
  11.000   1.4314   0.02950   0.02288  -0.0793   0.1030   0.7482
  11.250   1.4455   0.03053   0.02393  -0.0783   0.1004   0.7508
  11.500   1.4611   0.03145   0.02489  -0.0775   0.0983   0.7532
  11.750   1.4756   0.03246   0.02592  -0.0765   0.0959   0.7555
  12.000   1.4881   0.03364   0.02710  -0.0754   0.0932   0.7577
  12.250   1.5018   0.03476   0.02825  -0.0745   0.0912   0.7601
  12.500   1.5168   0.03578   0.02931  -0.0737   0.0894   0.7623
  12.750   1.5305   0.03692   0.03046  -0.0729   0.0874   0.7644
  13.000   1.5414   0.03829   0.03183  -0.0718   0.0853   0.7664
  13.250   1.5534   0.03959   0.03317  -0.0709   0.0834   0.7699
  13.500   1.5682   0.04066   0.03430  -0.0703   0.0819   0.7728
  13.750   1.5802   0.04200   0.03568  -0.0694   0.0801   0.7754
  14.000   1.5910   0.04345   0.03714  -0.0685   0.0783   0.7780
  14.250   1.5994   0.04510   0.03881  -0.0675   0.0763   0.7805
  14.500   1.6124   0.04641   0.04018  -0.0669   0.0752   0.7831
  14.750   1.6240   0.04782   0.04163  -0.0662   0.0738   0.7853
  15.000   1.6349   0.04931   0.04315  -0.0655   0.0723   0.7878
  15.250   1.6430   0.05110   0.04497  -0.0647   0.0707   0.7911
  15.500   1.6493   0.05305   0.04697  -0.0638   0.0692   0.7940
  15.750   1.6614   0.05449   0.04847  -0.0633   0.0681   0.7970
  16.000   1.6703   0.05625   0.05029  -0.0627   0.0669   0.8000
  16.250   1.6785   0.05808   0.05215  -0.0621   0.0657   0.8030
  16.500   1.6851   0.06008   0.05418  -0.0615   0.0644   0.8055
  16.750   1.6872   0.06260   0.05674  -0.0608   0.0630   0.8087
  17.000   1.6962   0.06440   0.05862  -0.0603   0.0622   0.8121
  17.250   1.7031   0.06646   0.06076  -0.0599   0.0613   0.8153
  17.500   1.7097   0.06857   0.06293  -0.0596   0.0602   0.8185
  17.750   1.7141   0.07093   0.06533  -0.0592   0.0592   0.8215
  18.000   1.7164   0.07355   0.06799  -0.0589   0.0582   0.8243
  18.250   1.7149   0.07664   0.07113  -0.0585   0.0572   0.8272
  18.500   1.7183   0.07918   0.07377  -0.0584   0.0565   0.8307
  18.750   1.7225   0.08168   0.07636  -0.0583   0.0558   0.8342
  19.000   1.7260   0.08427   0.07902  -0.0583   0.0550   0.8377
  19.250   1.7272   0.08716   0.08198  -0.0584   0.0542   0.8410
<< Back to NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il)

Polar data table (+)

Polar graphs


<< Back to NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il)